近/超临界RP-3航空煤油的喷射特性试验研究

葛浩; 范育新; 王伟利; 岳晨; 曹程皓; 刘易安

doi:10.13224/j.cnki.jasp.20220614

近/超临界RP-3航空煤油的喷射特性试验研究

doi: 10.13224/j.cnki.jasp.20220614

葛浩^1,,
范育新^1,*, ,,
王伟利²,
岳晨¹,
曹程皓¹,
刘易安²

1.
南京航空航天大学能源与动力学院，南京 210016
2.
北京动力机械研究所，北京 100074

基金项目: 国家两机专项（2017-Ⅲ-0007-0033）；先进航空动力创新项目（HKCX2020-02-020）；南京航空航天大学研究生科研与实践创新计划（xcxjh20210206，xcxjh20210210）

详细信息

作者简介:
葛浩（1997-），男，硕士生，主要从事航空发动机燃烧室方面的研究。E-mail：gehao0325@nuaa.edu.cn

通讯作者:
范育新（1967-），女，教授，博士，主要从事先进航空发动机燃烧技术方面的研究。E-mail：fanyuxin@nuaa.edu.cn

中图分类号: V231.2
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- 被引次数: 0
出版历程
- 收稿日期: 2022-08-23
- 网络出版日期: 2024-02-27

Experimental study on injection characteristics of near/supercritical RP-3 aviation kerosene

GE Hao^1
,,
FAN Yuxin^{1,*
, ,},
WANG Weili²,
YUE Chen¹,
CAO Chenghao¹,
LIU Yian²

1.
School of Power and Energy，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
2.
Beijing Power Machinery Institute，Beijing 100074，China

摘要

摘要:
针对未来先进航空发动机的超临界燃油喷射混合需求，采用纹影系统对近临界和超临界RP-3航空煤油喷射进入静止大气中进行了试验研究，并结合RP-3航空煤油10组分替代物对近/超临界燃油喷射过程进行解析。研究表明:近/超临界燃油喷射会产生激波结构，并且在喷口附近有相变过程，但是近临界和超临界喷射无论是在整体射流结构抑或是近喷嘴处射流结构上都有着不同，与近临界喷射相比，超临界喷射在马赫盘内气相区/液相区更大，再液化距离更长；同时随着喷射温度的增加，马赫盘直径和纵向距离以及射流扩张角均会减小，而随着喷射压力的增加，马赫盘直径和纵向距离以及射流扩张角均会增加。
- 近/超临界喷射 /
- RP-3航空煤油 /
- 10组分替代物 /
- 射流结构 /
- 相变
Abstract:
In order to meet the requirements of supercritical fuel injection for Advanced Aero Engines in the future, the schlieren system was used to conduct experimental research on the injection of near/supercritical RP-3 aviation kerosene into the still atmosphere, and the process was analyzed by combining with the 10-component substitute of RP-3 aviation kerosene. The results revealed that near/supercritical fuel injection could produce shock wave structure and phase transition near the nozzle exit. However, there were differences between near critical and supercritical jets in the overall jet structure or the jet structure near the nozzle. Compared with the near critical injection, the supercritical injection was larger in the gas-phase region/liquid-phase region in the Mach disk, and had a longer reliquefication distance; at the same time, with the increase of injection temperature, Mach-disk diameter, longitudinal distance and jet expansion angle all decreased. But with the increase of injection pressure, Mach-disk diameter, longitudinal distance and jet expansion angle increased.
- near/supercritical injection /
- RP-3 aviation kerosene /
- 10-component substitute /
- Jet structure /
- phase transition

HTML

图 1 超临界燃油喷射系统示意图

Figure 1. Schematic diagram of supercritical fuel injection system

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图 2 直射式喷嘴剖面图（单位: mm）

Figure 2. Section of direct nozzle （unit: mm）

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图 3 纹影成像系统示意图

Figure 3. Schematic diagram of Schlieren imaging system

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图 4 近/超临界燃油喷射区域划分图

Figure 4. Division diagram of near/supercritical fuel injection area

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图 5 欠膨胀波射流结构

Figure 5. Jet structure of under expansion wave

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图 6 超临界燃油喷射过程解析图

Figure 6. Analytical diagram of supercritical fuel injection process

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图 7 近/超临界燃油射流结构比较图

Figure 7. Comparison of near/supercritical fuel jet structure

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图 8 近/超临界燃油射流两相分析图

Figure 8. Two phase diagram of near/supercritical fuel jet

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图 9 近临界燃油射流结构比较图

Figure 9. Comparison of near fuel jet structure

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图 10 超临界燃油射流结构比较图

Figure 10. Comparison of supercritical fuel jet structure

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图 11 近/超临界燃油近喷嘴射流结构比较图

Figure 11. Comparison of near nozzle jet structure of near/supercritical fuel

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图 12 RP-3替代物密度和温度关系图（p_j=3 MPa）

Figure 12. Relationship between density and temperature of RP-3 substitutes （p_j=3 MPa）

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图 13 超临界燃油近喷嘴射流结构

Figure 13. Jet structure of supercritical fuel near nozzle

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图 14 马赫盘纵向距离与温度比和压比关系图

Figure 14. Relationship between the longitudinal distance of Mach plate and temperature ratio and pressure ratio

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图 15 马赫盘直径与温度比和压比关系图

Figure 15. Relationship between Mach disk diameter and temperature ratio and pressure ratio

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图 16 射流扩张角与温度比和压比关系图

Figure 16. Relationship between jet expansion angle and temperature ratio and pressure ratio

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表 1 RP-3的10组分替代物

Table 1. 10 component substitute of RP-3

分类	成分	摩尔分数/%
烷烃	正辛烷	6
	正癸烷	10
	正十二烷	20
	正十三烷	8
	正十四烷	10
	正十六烷	10
环烷烃	甲基环己烷	20
环烷烃	1,3-反式二甲基环戊烷	8
苯	丙苯	5
萘	1-甲基萘	3

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表 2 燃油喷注特性试验中的折合压力和折合温度范围

Table 2. Reduced pressure and temperature range in fuel injection characteristic test

参数	取值范围
燃油流量/（g/s）	3～9
p_j/p_c	1.172～1.548
p_j/p_a	28～37
T_j/T_c	0.963～1.084
T_j/T_a	2.12～2.39

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